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装在飞机上的发动机在超音速时的实际性能比理想发动机要来得小,在 M_o=2.0时推力损失可达20%或更大。如果此时有附加阻力的存在,发动机的可用推力还要小。而超音速飞机的需用推力在超音速飞行时随飞行 M 数的变化率与发动机可用推力随飞行 M 数的变化率很相近,因而可用推力的略为减小,会引起飞机性能的严重变化。超音速进气道在亚音速工作时也会引起很大的推力损失。如何提高实际可用推力及正确估计可用推力是超音速飞机设计中相当重要的问题,而改进进气压缩方式及提高进气口与发动机的配合性能在其中占了主要地位。本文按现有文献的若干成果,提出超音速飞机可用推力的计算方法;对进气道与发动机配合参数的若干方面也作了简单的介绍。本文主要涉及 M_o=2.0左右的超音速飞机,此类型飞机大多数采用外冲压式进气道;故也以此种形式为讨论的主要对象。采用其他形式进气道的飞机,其可用推力计算方法与外冲压式是类似的。
The actual performance of the engine mounted on the aircraft at supersonic speeds is less than that of the ideal engine, with thrust losses up to 20% or more at M_o = 2.0. If there is additional resistance at this time, the available thrust of the engine is smaller. The required thrust of supersonic aircraft with supersonic flight with the M-rate of flight and the available thrust with the rate of change of flight M-number is very similar, so the available thrust slightly reduced, will cause serious changes in aircraft performance. Supersonic intake in the subsonic work will also cause a great thrust loss. How to improve the actual available thrust and correctly estimate the available thrust is a very important issue in the design of supersonic aircraft, and the improvement of the method of intake compression and the improvement of the cooperation between the intake and the engine are the main issues. In this paper, based on the results of the existing literature, the calculation method of available thrust for supersonic aircraft is proposed. Some aspects of the parameters of the intake and engine are also introduced briefly. This paper mainly deals with supersonic aircraft with M_o = 2.0. Most of the aircraft of this type adopt external ram air inlet. Therefore, this form is also the main object of discussion. Aircraft using other forms of intake, the available thrust calculation method and the outer stamping is similar.